Axially opposed dual row jet reaction turbine



F. D. BUTLER Dec. 8, 1959 AXIALLY OPPOSED mum. ROW JET REACTION TURBINEFiled June 25, 1958 5 Sheets-Sheet l D m T w m F. D. BUTLER Dec. 8, 1959AXIALLY OPPOSED DUAL ROW JET REACTION TURBINE 5 Sheets-Sheet 2 FiledJune 25, 1958 4 "2m c c C n G o W H f I R Q 0 W ,r 2 w H F 5= wNEEH'IQEB Jim/56mm F. D. BUTLER De. s, 1959 AXIALLY OPPOSED DUAL ROW JETREACTION TURBINE Filed June 23, 1958 5 Sheets-Sheet 3 N LEYLNI QB:

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I I I Dec. 8, 1959 Filed June 23, 1958 LLLYELLIQEL MQWuM OUT-MESHINGIN-MESHIN G Dec. 8, 1959 BUTLER 2,915,876

AXIALLY OPPOSED DUAL ROW JET REACTION TURBINE Filed June 2a, 1958 5sheets-sheet s United States Patent AXIALLY OPPOSED DUAL ROW JETREACTION TURBINE Frank David Butler, Venice, Calif.

Application June 23, 1958, Serial No. 743,873 Claims. (Cl. 60-3935)While my invention relates to combustion turbines in general it appliesmore specifically to a new type of V- shaped, multiple annular rowaxially opposed, converging nozzled reaction jet type of expansioncombustion chambered, as combined with multiple annular row, increasingin capacities radially outward axially opposed, pressure velocitycompounded radial flow, curve bucket expansion chamber type of, internalcombustion turbine, provided with low volatile solid liquid fuelpressure atomizing and injecting, multiple expansion group controllable,flame type of non-smog-producing ignition, and, provided in conjunctionwith its respective elastic fluid compressor, and pressure variableratio reversible transmission coupler, in forming a unit motive powerassembly applicable as the motive power means of an automotive vehicle.

As illustrated herein my internal combustion turbine is used inconjunction with my multiple geared and pressure stage compoundedelastic fluid compressor, Patent No. 2,876,947, issued March 10, 1959,as its compressor, and my pressure variable ratio reversible, combinedtorque converter and automatically operative transmission coupler,Patent No. 2,799,182, as its respective coupler, in forming such unitmotive power assembly, and which latter is provided with an elongatedone direction rotative shaft extending throughout such assembly as thecommon driving means thereof. However as either such compressor and/orsuch coupler may be replaced by other similar means, neither will bedescribed in detail herein.

The major concept and improvement, as indicated and mentioned in theforegoing preamble of the specification,

is the provision the V-shaped, reaction jet type of axially pressurebalanced expansion, combustion chambers, which form the basis of theinvention as combined with the type of, similarly pressure balanced,pressure velocity compounding curved expansion chamber buckets as usedtherewith. In such turbine, two axially opposed annular inner rows of,relatively small, stator expansion chamber buckets are providedcooperative with the adjacent two axially opposed annular rows of outerends of said V- shaped combustion chambers; wherein at such location, 1

due to being divided up into expansion groups, such expansion chamberbuckets are incomplete as rows, are provided curved, in opposite todirection of rotor rotation and are each increased in length radiallyand in depth axially starting adjacent the ignition plug of theirrespective expansion group and extending, in the direction of rotorrotation, to adjacent the next expansion group fuel mixture diffusernozzle. Providing two methods of curved stator and curved rotor radialflow expansion chamber buckets that may be used in combination 7 withsaid V-shaped combustion chambers within the turbine, namely; thesemi-circular type buckets that may be machined diagonally axially intothe adjacent side faces of the turbine stator and turbine rotorrespectively,

in opposite to, and in the direction of, rotor rotation, and, i

2,915,876 Patented Dec. 8, 1959 ICC the conventional axially extendinginserted blading type, in which latter the stator and rotor bladebuckets are respectively inserted into the adjacent side faces of theturbine stator and turbine rotor and are respectively curved, inopposite to, and in the direction of, rotor rotation. Providing in bothtypes of adjacent annular shaped rows of expansion chamber buckets thatthe capacities thereof increase radially outward in both the stator androtor, with said two opposed incomplete inner rows of stator bucketscooperative with the adjacent outer ends of said V-shaped combustionchambers as previously mentioned. Providing two opposed rows ofelongated axially extending radial exhaust slots, one row in each statorhalf, which each connect the adjacent outer row of rotor buckets with anadjacent exhaust cavity in each such stator halves. Providing anelongated one direction rotatable turbine rotor shaft which extendsaxially within and is the common driving shaft of the entire unit motivepower assembly, including the turbine, its elastic fluid compressor andits reversible power delivery transmission coupler. Providing a meansfor braking such coupler, also a means, attached to such braking meansfor driving a speedometer cable. Providing a Worm operative by saiddriving shaft for operating a diaphragm type fuel supply pump, and ageared type of solid fuel injection pump through a worm-wheel and itsextension shaft. Also providing a manually operative combined controland distributing unit, provided with an insulated quadrant, forsimultaneously controlling the distribution of compressed elastic fluidand ignition electricity to the expansion groups. of the turbine, aswell as controlling the lift of a spring-loaded solenoid coil operativefuel metering valve, which latter supplies a measured quantity of solidfuel, through a pressure atomizer to within said distributing unit, inproportion to the quantity of compressed elastic fluid being deliveredtherethrough to said turbine.

Also unique additional minor improvements as will be disclosedhereinafter as the specification description progresses.

With reference to the figures of the drawings: Fig. 1 is a longitudinalsection through my semi-circular bucket type of, dual radial flowpressure velocity compounded turbine as on the dotted line 1-1 of Fig.7; Fig. 2 is a detail elevation as along the dotted line 2-2 of Fig. 1;Fig. 3 is detail sections, in plan, as along the plurality of dottedlines 33 of Fig. l and illustrate less angle of inner than of outerbuckets; Fig. 4 is an enlarged plan section of the V-shaped reactioncombustion chambers, and dual opposed expansion groups as along theradius of the dotted line 4-4 of Fig. 1; Fig. 5 is jointly in frontelevation and in a series of transverse sections of the unit motivepower assembly, Fig. 6, with the lower right in broken away frontelevation, then reading clockwise, with the adjacent 90 section as onthe dotted line 5-5 of the turbine, the adjacent 90 section as on thedotted line 55 of the compressor, and, the adjacent 90 section as on thedotted line 55 of the coupler; Fig. 6 is a joint plan and section of theunit .motive power assembly as mounted in an automotive vehicle framingand as taken along the dotted and broken line 66 of Fig. 7; the latteris a miniature front elevation of the assembly of Fig. 6, and wherein Ais a. detail longitudinal section through the turbine combined exhaustpipe and air diifuser muffler; Fig. 8 is a diameans for supplying fluidunder a variable pressure to .within the coupler of Figs. 5, 6 and 8;Fig. 13 is a sectional view through the combined compressor regulatorand the solenoid coil operative fuel metering valve; Fig-'14 is asection in plan through Fig. 15 on the dotted ,line 1414 thereof, andillustrates the diagonally exlending communication slot extendingthrough a bafiie partition from the inmeshing sides of the adjacentlower pressure stage to the outmeshing sides of the adjacentfhigherpressure stage gearing of the compressor; Fig. 15

is a transverse section on the dotted line'15- -15 of Fig.

'14; Fig. 16 is a detail of thecombined multiple disc strainer andoutlet check-valve of the compressor accumulator manifold; Fig. 17 is adiagrammatical illustration of a compressed elastic fluid startingcircuit means 'for the turbine; Fig. 18 is a longitudinal sectionthrough- 1 out the-combined turbine control and distributing unit, while'theinsert A is a transverse section on the dotted line A''A through theelectrical potentiometer for controllingthe solenoid coil operative fuelmetering valve,

and also through the electrical contacts for grounding the "ends of theprimary windings of three vibrating contact point primary, nongroundedsecondary, ignition induction coils (not illustrated) which each maysupply two ignition plugs simultaneously; Fig. 19 is a longitudinalsection through the relatively more expensive inserted 'bucket type of,dual radial flow pressure velocity compounded turbine as on the dottedline 19-19 of Fig. 20; and, the latter is a broken awayend elevation andtransverse section as on the dotted and broken line 20-20 of Fig. 19 andillustrates the detail of cooperation between the combustion chambersand the stator and rotor buckets of the turbine.

.With reference to the symbols of the drawings, similar :symbolsrepresent and indicate similar parts in the several figures: The numeral1 indicates the'elongated rotor shaft which extends throughout the unitmotive power assemblyas the common driving shaft thereof for rotativelydriving the multiple staged driving gears DG, D6 and DG" of the multiplepressure staged compounded elastic fluid compressor 3, and the sun-gearSG of the a? 'quadruple" planetary geared compounded, pressure'variableratio reversible, transmission coupler 5. This shaft 1 is rotativelyjournalled upon the opposed pair of adjusjtable roller bearings 1B and'IB (Fig. 6) concentrically with'the 'axially opposed rows ofopen endsof the, V-shaped combustion chambers CC of the turbine rotor 1R, theaxially opposed rows of different lengths jjof stator buckets 2B of theopposed turbine stators 2 and 2";of the turbine stator 2, the elongatedbore 3B of the compressor body 33, and, to the coupler casing 5C, andisalso'journalled upon the set of needle bearings 4NB, in the couplerstator 45, and the adjustable roller bear- ,ing 5B in the rear end ofsaid coupler casing 5C. The latter is rotatively journalled upon saidstator 48 and .said shaft 1 respectively upon the opposed pair ofadjustable roller bearings 5B and 5B','which latter is .provided withthe tongued locking washer 5W and the adjustment nut'SN. Thecoupler endof said shaft 1 is provided with the external helical spline 11-18 which-rotatively drives the coupler sun-gear SG and also pro- :vides thelatter and the coupler planet-gear-carrier PGC with an axial thrust tothe right in Fig. 6. The intermediate portion of'said shaft 1 isprovided with a spline 1S 7 DG may be provided with a worm W (Figs. 5, 6and 9) for rotatively driving the fuel pumps.

With reference to Figs. 1 to 7 inclusive, the radially extendingdisc'shaped turbine rotor IR is secured to rotate in one direction withthe shaft 1, between the pair of opposed diverging stator halves 2 and2", and is provided with: a row of series of V-shaped combustionchambers CC with the ends thereof each extending from the adjacent sideof said rotor convergingly, in the direction of rotor rotation, to thecenter of the width of such rotor at which point they unite; a pluralityof series of opposed rows of similar semi-circular shaped progres sivelyincreasing in length and depth and diagonal pitch angle radially ofrotor expansion chamber buckets 1b, machined into the opposite sides ofthe rotor in the di rection of its rotation and with the inner ends ofthe smaller of such buckets originatinga relatively short predetermineddistance outward radially from the adjacent ends of said combustionchambers CC, and with the outer ends of the largest of such buckets 1bterminating closely adjacent to the periphery of said rotor; a pluralityof rows of diagonally axially extending air circulating holes CHextending through said rotor inward radially from said combustionchambers; an air circulating blower AB provided with a series ofdiagonally axially extending multiple vanes and a hub portion securedover and shouldered against the front hub end of said rotor; a combinedmultiple V-grooved pulley VP and air circulating blower secured adjacentthe front face of said front hub of said rotor by the tongued lockingwasher 1W and the securing nut 1N of such rotor; the

key K for shaft 1, pulley VP and rotor IR; and, a series of snap-ringtype of non-rotative fluid seal rings SR disposed externally in the rearhub portion of said rotor.

.With reference to Figs. 1 to 7 inclusive, the turbine .stator isconstructed in two annular shaped, radially diverging, axially opposedhalves 2' and 2", which are bolted together and secured concentricallywith and to the compressor inlet manifold IM by the series ofsymmetrically' spaced bolts 2b, and fit closely-along their divergingsides with the adjacent sides of said rotor 1R,

a'ndar'e each provided with: a series of opposed rows of similarsemi-circular shaped turbine expansion cham- ,ber buckets 2B, whereineach adjacent row of buckets increases in length and depth and diagonalpitch angle .radially outward, and wherein each bucket is machined intoits respective opposed stator in opposite to the di rection of rotorrotation, and with the inner ends of the smallest buckets originatingadjacent the opposed open ends of said combustion chambers CC and eachopposed row offsuch opposed statorbuckets 2B extending radially outwardalmost to the center of the length of the next larger row of rotorexpansion chamber buckets 1b; a row of series of axially extendingelongated radial exhaust slots ES, located in each stator half 2' and2'',

which slots connect the outer half of the largest rotor bucketsv 1b withthe adjacent exhaust cavity EC of its respective stator half; means forbolting an exhaust manifor ro'tatively driving the previously mentioneddriving fold EMto both of such stator halves, and which manifold isconnected to an exhaust pipe EP which latter isformed into a combinedexhaust diffuser silencer and excess'air induction mufiier M, Fig. 7-A,that requires no exhaust tail pipe and mixes the exhaust gas with heatedair which results in an upward draft whichtends to eliminate smog; and,a series of radially extending cooling finsCF, integral with each statorhalf.

The front stator half 2, is provided with a series,- of Six in theexample case illustrated, of paired fuel supply diffuser nozzles DN andignition plugs IP, which each .extendsthrough such front stator half andterminates adjacent the front ends of .the' adjacent V-shaped combustionchambers CC and divides the turbine into six,-in the example case,ofidual opposed pressure velocity compounding-expansion groups, whereinthe inner rows of opposed stator buckets 2B'are not continuous and areincreased in length and depth progressively in an are starting adjacentthe respective group ignition plug IP and extending, in the direction ofrotor rotation, to adjacent the next group diffuser nozzle DN, asillustrated in Figs. 1 and 4.

In my compressor, US. Patent No. 2,876,947, issued March 10, 1959, the1st, 2nd and 3rd stage driving gears and series of pinion gearsrespectively DG, DG and DG meshing with PG, PG and PG", are allrotatively journalled and mounted within the compressor body 3B, asillustrated in Figs. 5 and 6; while 3B, including the annular stagediaphragms PP and PP are secured, concentrically between the front coredinlet manifold IM and rear cored accumulator manifold AM, with theseries of elongated, hollow, combined journal and securing bolts JB;and, the interstage suction and discharge ports of the compressor arecontained within the compressor.

In my coupler, U.S. Patent No. 2,799,182, issued July 16, 1957, thereare two sets of tandem paired compounding planet-gears IPG-ZPG, 3PG-4PGand 5PG-6PG, with the sets located 180 apart as in Fig. 8, all carriedin planet-gear-carrier PGC, with 1PG meshing with SG and 6PG meshingwith orbit gear G; with fluid circulation in as indicated by arrows Fig.6; at turbine idling speed, PGC may be variably pressure braked againststator disc SD, thereby reversing OG, while at above idling speeds, PGCmay be variably pressure clutched against 5C; and, wherein such couplerthe variable range in reverse rotation extends from 1,000 to 1, to 32 to1 ratio, while in forward rotation it extends from 1,000 to 1, to a l to1 ratio, and, is a torque converter in forward rotation.

The coupler casing 5C is provided with a row of series of aircirculating fins SP for inducing cooling air from the turbine stator 2through the hollow bolts IB, and from adjacent IM through the axial aircirculating holes H3 in 313' and AM. Such casing 5C is also providedwith an emergency brake drum BD, secured to its rear and/or right endFig. 6, and also a universal joint U] secured to such end, and, whereinU1 is provided with a worm W, external thereto, for rotating awormwvheel WW which latter rotatively drives the speedometer cable SC,which latter rotates relative to delivery speed of the coupler.

With reference to Figs. 6, 7 and 13, the carburetor 6, may be providedwith an electrical heating element which may be located under thecarburetor bowl and be operated by the electrical potentiometer EP,which latter is operated by the throttle-valve-stem TVS, and whichheater, would be for reducing the viscosity of the fuel in 6. The lattermay also be provided with a similar potentiometer EP similarly operatedby TVS and for operating the solenoid coil Sc of the fuel metering valveFM for supplying surplus fluid under pressure from the base of AM to thepressure atomizer PA, and through the latter injecting it back intosuction of compressor 3. The throttle-valve-stem TVS is operated by thecompressor regulator PR, which latter may be connected to theaccumulator manifold AM, on one side of its piston P, by the connectiontubing CT and is spring-loaded on the opposite side of P and connectedby the spring-wire SW to the bell-crank BC of TVS. Thus whenever thepressure of the surplus fluid from AM is less than the springloadsetting of PR, then the piston P opens the throttle valve-stem TVS andsimultaneously reduces the grounding resistance of EP and EP, so thecarburetor heater is placed into service and the solenoid coil Sc of thefuel metering valve FM opens such valve and surplus fuel is injectedthrough the pressure atomizer PA into carburetor 6 below TVS, and viceversa if such spring-load setting is exceeded by the pressure in PR.

With reference to Figs. 5, 6, 7 and 16, the combined outlet check-valve8CV and adjustable strainer 88D is operated by the electrical solenoidcoil 8SC as follows:

'6 Whenever the primary electricity of the ignition supply is placedinto service and the pressure in the accumulator AM is above apredetermined pressure, then 8SC opens 8CV, and compressed elastic fluidmay flow from AM through supply tubing ST7 into the control distributingvalve 7D, and vice versa.

While the motive power assembly is normally started by the 12 volt D.C.electrical motor generator MG, it may simultaneously be started withcompressed elastic fluid from reservoir 78K (Fig. 17) providing theelectrical supply to MG and to the solenoid coil 78C of the check-valve7CV are in parallel and/ or the turbine may be started by suchcompressed elastic fluid alone through operation of the push-button 7PB.Such pressure starting means may consist of At any time while theturbine is in operation the reservoir 78K is charged from theaccumulator AM through check-valve 8CV, thence supply tubing ST7, thencecontrol valve 7D, thence tubing 7T, thence past ball-check valve 7BC7,and, into 7SR. Thus assuming that the pressure in. AM is too low to opencheck-valve 8CV when electricity is supplied to the ignition system andsimultaneously to solenoid coil C and said push-button 7PB. Thenoperation of the latter would result in compressed elastic fluid beingreleased from 7SR past the check-valve 7CV and through tubing 7T intothe control valve 7D. Once the turbine started rotating, ignition of thecombustion charges in chambers CC (Fig. 4) would be by direct flamecontact within the spark-gap collars IPC.

The carburetor 6 is supplied with diesel fuel by the usual typediaphragm pump DP (Fig. 10), which along with the rotary geared pump RGP(Fig. 11) is operated by the shaft 1 through the worm W and worm wheelWW (Fig. 9) rotating the pump drive shaft PDS, which latter rotates thedrive-cam DC for pump DP, and the drive-gear Dg of the pump RGP, and,wherein Dg rotates the rotor gear RG. In practice either one of twomethods of fuel supply may be used. In the first method, all the fuelused would be induced into the compressor 3 from the carburetor 6through the inlet manifold IM, and any solid fuel accumulated in thebase of the accumulator manifold AM would be pressure atomized andinjected back into 6 beneath its throttle valve stem TVS, as previouslydescribed. This would insure ample lubrication of the compressorgearing. In the second and/ or preferred method the carburetorspray-nozzle would be blanked off, atomizer PA would not be used, andonly filtered air would pass through the throttle valve. The base of AMwould then be used for supply of a vegetable lubricating oil such ascastor and/or olive oils which would be recirculated within compressor3. The pump RGP would then take diesel fuel suction from the bowl of 6and would discharge through the fuel metering valve FM (Fig. 13), andthe pressure atomizer PA (Fig. 18) into the end of the control valve 7D.The solenoid coil S0 of valve FM would then be controlled by thepotentiometer EP (Fig. 18) which may be made variable by a remotelycontrollable variable resistance in series between Sc and EP", while thedischarge pressure of pump RGP would be limited by the setting of therelief-valve RV thereof, and, wherein other factors to be consideredwould include the size of the orifice in PA, the adjustment setting ofFM, and the capacity of the resistance of EP.

With reference to Figs. 1 to 7 inclusive and 18, the turbine control anddistributing valve 7D is operative by the usual foot accelerator of anautomotive vehicle, and is a means for controlling the number of fueldelivery diffuser nozzles DN and ignition plugs IP that are placed intoand/ or out of service, and simultaneously controlling the metering ofthe quantity of atomized solid fuel that Will be injected into thecompressed fuel mixture that is proportioned within said valve 7D inaccordance with the number of such nozzles placed into and/or out ofservice thereby. With reference to Figs. 18 and l8-A',

the combined control and distributing van/e 7D ass; sists offanelongated cast body' portion '7Bprov1ded withan elongated central bore7B having a reduced bore .7b iii tandem therewith at one end thereof,provided with an adjustable packing gland 7G, anda pressure fuelatomizer PA adjacent its opposite end, with a plurality of radiallyextending progressively openable and/ or closable fuel delivery'tubingfittings PD and a pair of non closable oppositely located tubingfittings ST7 and 71 all located intermediately to the ends thereof andopen- :ing into saidbore 7B; an elongated stepped diameter piston7P withthe larger diameter portion slidable with]- in bore 7B and the smallerstep diameter portion slidablewithin gland 7G and provided with'a seriesof symmetrically spaced communication holes 7P extending longitudinallythrough the larger diameter portion thereof, and wherein such piston isnormally displaced away {from said atomizer PA by elastic pressure andis displaced towards said atomizer PA manually by the bellc'rank'7BC,and is limited in the latter displacement by a snap-type stop ring 7SRwhich is located in bore 7B adjacent an enlarged annular shaped recess7AR connecting fittings ST7 and 7T; wherein said bell-crank 7BC ispivoted ina forked end of the body portion 7B, is manually oscillatableby the reach-rod 7RR, is limited in its piston-valve opening travel bysaid stop ring 78R,

is stopped in its piston-valve closing travel by the turbine idlingstop-screw 71S, and, is provided with a plurality of spring-loadedelectrical contacts 7C and 7C respectively for grounding the primarywindings'of the three ignition induction coils previously mentioned, andwherev in 7C is for grounding the potentiometer EP"; and, anon-oscillatable electrically insulated quadrant 7Q, se

cured to 7B, containing thev grounding terminals 7GT of the primarywindings of said ignition coils and the potentiometer EP". With furtherreference to distributor 7D,1 the followingshould be noted: the fittingsFD are arranged in an opening sequence of FDI, FD4, FDZ, FD5, FD3and'FD6; while the ignition coil grounding terminals GT, in the quadrant7Q, are in the sequence of GT1-4, GT25and GT3-6; and, that two ignitionplugs.

IP are thus placed into and/or out of service simul taneously. Thus itis apparent, that under turbine idling conditions ofoperation, onlyfitting FDI and its respective fuel diffuser nozzle DN would be inreduced service, i

and only GT1-4- and their respective ignition plugs IP would be inservice along with the 1st duel pressure Velocity compounding expansiongroup of the turbine,

while the compressed elastic fuel mixture within the V shaped combustionchambers CC would be under direct flame contact (continuous train typeof) ignition. Further movement of 7BC and piston 7P to the right Fig. 18 would place FD4 and its respective diffuser nozzle DN in service alongwith the 2nd dual pressure velocity compounding expansion group of theturbine. During Suchmovement of 7BC and 7P, the spring-loaded contact7C,'in 7BC, would tend to place terminal GT25 into and GT1 -4 out ofservice, and simultaneously the springloaded contact 7C would bedecreasing the grounding resistance of the potentiometer EP which wouldresult in increasing the magnetic lift power ofthe solenoid coil S y-ofthe fuel metering valve FM (Fig. 13), so a greater quantity of fuelwould be atomized and injected, through i the pressure atomizer PA, intothe right end of the control valve 713 in proportion to the number offittings PD]. 1

and FD4 in service; and, vice versa as 7BC and 7P are manually moved tothe left in Fig. 18 by the reach rod 7RR. In order that the turbine maybe started on a rich mixture and then reduced to a relatively leanmixture, a remotely operable variable resistance may be inserted inseries between Sc and EP". 7

In order to attain supremacy in dual radial flow,

axially pressure balanced, pressure velocity compounded turbines, thelatter maybe constructed as in Figs. 19

and20 an d maybe manufactured as follows: the turbine 8 rotor buckets1b, stator buekets'ZB', annular shaped stator rings 2'R and 2"R androtor'lR'may all be of nickel, chrome-molybdenum and/or stainless steelmetal; the similar buckets lb' and'ZB' may all be machined fromhot-rolled and formed lengths'of bucket materials and each be providedwith a cylindrical pilot end and an adjacent circumferentially extendings'erration as illustrated; the stators 2' and 2? may be made of Duralmetal, and the annular shaped grooves machined therein and in the sidefa'ces of the rotor 1R should be serrated and of less width than thestator buckets thereof so as to produce reaction expansion within theturbine buckets, see

right side of Fig. 20; such buckets should then be assembled in theirrespective stator or rotor by first pressing each bucket into itsrespective pilot hole, until it rests upon its respective groove'slotbase, then rotating it into the adjacent serrations in the sides ofsuch groove; after all buckets are rotated into place, then the rotorbuckets 1b may all be hard soldered to flush with depth of grooves,while the buckets 2B may all be heliarc welded, similarly flush withdepth of grooves, and thereby to abolish the T-shaped relativelyexpensive type of buckets; the heat resisting annular shaped statorrings 2'R and 2"R may each be secured within their respective stators2"and 2" by the socket headed cap-screws 2b, both of such rings beingprovided with a series of increasing in lengths of semi-circular shapedcurved stator buckets 2B" with one series for each expansion group ofthe turbine, and with only the front'ring 2'R provided with a diagonallyaxially through extending diffuser nozzle DN and an adjacent throughaxially extending ignition plug spark-gap recess therein for each suchexpansion group; and, so that all fuel delivery fittings PD and ignitionplugs IP may extend axially through stator 2, While the worm W may belocated between the gear DG and the snap-ring 1r over the spline 18 ofthe rotor shaft 1, extending throughout the unit motive power assembly.

Assuming the displacement of the 1st stage drive gear DG' to be, eachrevolution thereof, by formula: Teeth in DG length DG width of eachtooth on pitch line working depth of each tooth X (2 x number of piniongears PG); substituting we have 72 3.5" 20=236.2 cubical inches ofdisplacement each revolution of DG. Now assuming the compressor deliversthe compressed elastic fluid to the accumulator under 11 atmospheresand/or 14-7 lbs.

gauge-pressure, thus there would be about 236.2/1 1:215

cubical inches of compressed fluid delivered under 147 lbs. gaugepressure during each revolution of DG. Now assuming that there are 48V-shaped combustion chambers CC in the turbine rotor 1R, thus therewould be 48 twin explosions for each diffuser nozzle DN during eachrevolution of IR. Then as there are six diffuser nozzles with an axiallybalanced twin expansion group for each DN, we would have 288 explosionsand 576 expansions during each revolution of IR. Each combustion chamberCC should be 21.5/2 88 .075 cubical inch in capacity. Thus due to directflame contact ignition and the relatively high delivery pressure of 147lbs. on the elastic fuel mixture, the turbine should operate undernon-smog CO (carbon dioxide) exhaust at all operating speeds while usingatomized solid diesel fuel injection.

Normally the unit motive power assembly could be supported from thevehicle framing F upon two forward FE and two rear RB brackets with therear end slightly FP", which latter are each welded to framing F. Atleast the top of the coupler casing C shold be protected with a shield58 secured to manifold AM.

Having fully described my invention in one of its best methods ofadaption, in conjunction with a unit motive power assembly, to anautomotive vehicle, I claim:

1. The provision in an internal combustion turbine of: a radiallyoutward extending one direction rotatable turbine rotor that is providedon either side face thereof with a series of adjacent annular rows ofprogressively radially outward increasing in diameters of semicircularshaped rotor expansion chamber buckets with each row machined at anangle to the adjacent side face of the rotor into the latter in itsdirection of rotation and with the machining angle of each adjacent rowprogressively increasing towards the rotor periphery; an annular row ofseries of axially extending V-shaped combustion chambers with the endsthereof each extending diagonally convergingly into the side faces ofsaid rotor in the direction of rotation of the latter and terminatinginto each other and forming a row of combustion chambers on either sideof said rotor inward radially a predetermined distance from the smallestdiameter rotor buckets; a radially outward diverging extending axiallyhalved type of turbine stator that is provided on each adjacent sideface thereof with a series of adjacent rows of progressively radiallyoutward increasing in diameters of semi-circular shaped stator expansionchamber buckets with each row machined at an angle to the adjacent sideface of the stator into the latter in opposite to the direction of rotorrotation and with the machining angle of each adjacent row progressivelyincreasing towards the rotor periphery and wherein all such rows ofstator buckets, excepting the inner-most row, extend from approximatelycenter to center of the adjacent rows of rotor buckets, while said innerrow connects the combustion chambers and smallest rotor buckets; aplurality of rows of series of axially extending radial exhaust slotswith one row .in each stator half outward radially from the adjacentlargest diameter row of stator buckets and oppositely axially from theadjacent outer one-half of the largest diameter row of rotor buckets andeach provided to connect the latter with an adjacent exhaust cavity;means in the form of a row of series of fuel mixturediffuser nozzles,located in one-half only of said halved stator and which divide theturbine into expansion groups and are for supplying fuel mixture to eachof said com- ,bustion chambers in a predetermined manner; means in theform of a row of series of ignition plugs one located in the directionof rotor rotation a predetermined distance from each of said diffusernozzles and for igniting fuel mixture in each of said combustionchambers in a predetermined manner; and, a jointly operative manualmeans for controlling the distribution of the fuel mixture to saiddiffuser nozzles and the ignition supply to each of said ignition plugsin a predetermined sequence manner.

2. The internal combustion turbine of claim 1 characterized by, whereinthe innermost row of all of such rows of stator buckets in each half ofthe turbine stator consists of: dividing each innermost row of statorbuckets in each such stator half into paired axially opposed expansiongroups with one group of each pair of groups located oppositely in eachhalf of said halved stator and wherein each paired group is providedwith one fuel mixture diffuser nozzle and an adjacent ignition plug andwherein each such inner row of stator buckets are relatively smaller incapacity starting adjacent the group ignition plug and increase incapacity in the direction of rotor rotation to adjacent the nextpreceding expansion group.

- 3. The internal combustion turbine of claim 1 characterized by, saidmeans in the form of a row of series ,ofdual mixture diffuser nozzlesand said means in the and axially extending ignition plugs, each openinginto one row of ends of said series of combustion chambers and whereinthe turbine is divided into a series of axially oppositely located twinexpansion groups on either side of said rotor, wherein each twin groupis provided, in the direction of rotor rotation, with one diffusernozzle and one ignition plug and wherein such an arrangement providestwin group expansion within the turbine.

4. The internal combustion turbine of claim 1 characterized by, saidmeans for controlling the distribution of fuel mixture and ignitionsupply to consists of: an elongated control and distributing valve unitprovided with an elongated bore closed at one end by a reduced diametergland and at its opposite end by a liquid fuel pressure atomizer, andprovided, adjacent the latter, with an annular shaped recess surroundingsaid bore, and a round annular shaped snap-ring located in a grooveadjacent the opposite side of said recess within said bore, and providedadjacent said recess with a tubing connection to a compressed elasticfluid supply means, and, also a tubing connection to a pressure startingreservoir; an elongated piston provided with a reduced diameter stem endslidable within said gland and a hollow enlarged opposite end slidablewithin said bore; a manually operated short and long armed bell-crankpivoted in a forked end of said unit adjacent the gland end thereof andlimited in its manually operated long arm arc travel by said pistonstriking said snap-ring, and limited in its opposite, pressure actuated,travel by the short arm contacting an adjustable turbine idling stopscrew located in said forked end of said unit; a series of radiallyextending tubing connections secured in such valve unit and eachprovided with an access arranged in said bore in such manner as to beprogressively opened and/or closed during the slidable travel of saidpiston and wherein each of said tubing connections leads to one of saiddiffuser nozzles; an electrically insulated quadrant piv-- groundingterminals located at less radius arc travel of and contactable by asimilar spring-loaded contact therein said long arm, and, wherein thepotentiometer is connected to a solenoid coil operative fuel meteringvalve for supplying fuel to said atomizer, while said groundingterminals are each connected to the primary windings of separateignition coils for supplying ignition electricity to each of saidignition plugs.

5. An internal combustion turbine having an axially halved type ofannular shaped stator, the provision therein of: a relatively narrow onedirection rotative radially extending rotor provided on both sidesthereof with a series of annular rows of rotor buckets curved in thedirection of rotor rotation and provided increasing in capacitiesradially outward; a series of through axially extending V-shapedcombustion chambers with the ends thereof each extending diagonallyconvergingly into the sides of said rotor in the direction of rotationof the latter and terminating into each other and forming a row of suchchambers, open at their larger ends to the sides of said rotor, apredetermined distance inward radially from the inner row of said seriesof rows of rotor buckets, on both sides of said rotor, and each capable,of a jet type of reaction diffusion of products of combustion during thenormal rotative operation of such turbine rotor; and, a plurality ofrows of through diagonally axially extending air circulating holeslocated,

' narrow one direction rotative radially'extending rotor,

theprovision therewithof: Ian axially halved type, of annularsha'pedturbine stator provided with itsperiphery "closed and its innerradius concentrically supported,'-'in' relation-to the axis ofrotation-of said rotor, upon a compressor member ofsuch turbine, andprovided on the adjacent sides of such stator with a series of annularrows of stator buckets c'u'rved in opposite to the direction of rotorrotation and provided increasing in capacities radially outward; aplurality of rows of axially extending radial exhaust slots with one rowlocated outward radially from each outer row of stator buckets andeachrow of such slots provided for forming a baffled access extendingbetween an adjacent row of rotor buckets of said rotor and an adjacentexhaust cavity in said stator; a row of paired fuel mixture difiusernozzles and ignition plugs symmetrically spaced about the rotor axis andrespectively extending diagonally axially, 'in the direction of rotorrotation, andaxially through, one halfonly of such stator and pairs ofsuch nozzles and plugs terminating in a row a predetermined distanceapart from one another adjacent the inner row of stator buckets in suchrespective half of such stator and respectively pro- -'vided forsupplying a' difiused compressed elastic fuel mixture to within each ofan adjacent row of, through extending combustion chambers, located in anadjacent side of said rotor, and for initially igniting such mixturewithin'each such combustion chamber within said rotor, and also providedfor forming expansion groups within the turbineia plurality of rows ofaxially extending radial cooling fins with one row extending integralextjernally with each half of said stator; and, means for connecting anexhaust manifold, located radially outward externally to such statorhalves, with each'of such extion, exhaust difiuser mufiler. j

7. An internal combustion turbine provided with? a relatively narrow onedirection rotative radially extending turbine rotor provided on bothsides thereof with a series of annular rows of rotor buckets witheachbucket curved in the direction of rotor rotation and provided haustcavities and to a self activating, excess air inducincreasing incapacities radially outward; a series of I through axially extendingV-shaped combustion chambers with the opposite ends thereof eachforminga row located on each side ofthe rotor and each end of eachcombustion chamber extending diagonally convergingly into the adjacentside of said rotor in the direction of rotation of the latter andterminating together at the point of the Vtherein such rotor and whereineach opposite end of each combustionchamber is capableof a jet type ofreaction diffusion thrust from the'expanding products of combustionduring the normal rotative operation of such turbine rotor; a'pluralityof rows of through diagonally axially extending air circulating holeslocated within said rotor inward radially from said rowoeeombustionchambers; an axially halved type of annular shaped turbine statorprovided with its periphery closed and its inner radius concentricallysupported,"in relation 'jacent inner row of rotor buckets and do notform a to the axis of rotation of said rotor upon an elastic fluidcompressor member of and for such turbine,'and provided on the adjacentsides of 'such statorwith a series of rows of stator buckets curved inopposite'to the direction of rotor rotation'and cooperative with theadjacent rows of rotor buckets; a plurality of rows of axially'extending radial exhaust slots with one row located outward radiallyfrom each outer row of stator buckets within such halves of such statorand each row of such slots 7 provided for forming a baflied accessextending between the adjacent outerrow of rotor buckets of said-rotorand an adjacent exhaust cavity inrthe respective stator, half; a row ofpaired fuel mixture difiuser nozzles and ignition plugs with each pairspaced a predetermined distance apart from one anothersymmetrically'about the rotor axis, thus dividing the turbine .into.expansion groups, andrespectively' extending diagonally through,

in the direction-ofrotor rotation, and axially through onehalf only ofsuch stator and terminating in a row internal to such stator halfadjacent to the inner row of stator buckets thereinjand. respectivelyprovided for supplying a diffused compressed elastic fuel mixture towithin the adjacent ends of said combustion chambers within said rotor,and for initially igniting such mixture within each such combustionchamber within such rotor; a plurality of rows of axially extendingradial cooling fins with one row extending integral externally with eachhalf of said stator; means for securing such halved stator to saidcompressor member and including means for rotatively supporting a shaftof said rotor concentrically rotative therein such compressor member;means for connectingan exhaust manifold, located radially outwardexternally to such stator halves, witheach of such exhaust cavities andto a self activating, excess air induction, exhaust diifuser mufiier;and, a jointly operative externally located manual means for controllingthe number of fuel mixture difiuser nozzles and ignition plugs that areplaced into and/or out of service progressively and for simultaneouslyregulating the amount of atomized solid fuel that will be injected intothe compressed elastic fluid that is supplied through such jointlyoperative means proportionally to the number of fuel mixture difiusernozzles that are placed into and/or out of service through such jointlyoperative means.

8. The internal combustion turbine of claim 7 characterized by, thecurved rotor buckets and curved stator buckets of the turbine to consistof a series of annular rows of axially extending radially curved, in thedirection of rotor rotation, of increasing in capacities radiallyoutward, of inserted type of rotor buckets secured in axially extendingserrated grooves machined in the sides of said rotor and wherein eachsuch row of inserted type of rotor buckets cooperate with an adjacentannular row of series of similarly axially extending radially curved, inthe opposite direction to rotor rotation, of similar type of insertedstator buckets, similarly increasing in capacities and similarly securedin axially extending serrated grooves, exceptingwith latter machined inthe adjacent sides of each of such stator halves, and, wherein the innerrow of stator buckets in each stator half of the last mentioned statorbuckets are curved and connect the adjacent combustion chambers with theadcontinuous row of these stator buckets in either of such statorhalves, and wherein the axial bucket clearances should be at apredetermined minimum clearance tolerance.

9. An internal combustion turbine comprising: a relatively narrowradially extending one direction rotative turbine rotor provided on bothsides thereof with a series of annular rows of increasing in capacitiesradially outward of rotor expansion chamber buckets each curved in thedirection of rotor rotation; a series of V-shaped combustion chamberssymmetrically spaced around the axis of rotor rotation and eachextending from opposite sides of such rotor diagonally axiallyconvergingly in the direction of rotor rotation as twin tapering nozzlesterminating together in the middle of the width of such rotor andforming an annular row of open ends of such combustion chambers on eachside of such rotor with each row located a predetermined distance inwardradially from the adjacent inner annular row of said rotor expansionchamber buckets; a plurality of annular rows of through diagonallyaxially extending air circulating holes located within said rotor inwardradially from said annular rows of combustion chamber ends; axiallyhalved type of annular shaped turbine stator provided'with its peripheryclosed and with both of its adjacent sides provided with a series ofannular rows of increasing in capacities radially outward of statorexpansion chamber buckets each curved in opposite to the direction ofrotatio'ntof said/rotor and cooperative with the adjacent annular rowsof rotor expansion chamber buckets,"and, wherein the inner' row of suchstator buckets of each stator half is not continuous and connect theadjacent row of combustion chamber ends with the adjacent inner row ofrotor buckets; a plurality of rows of axially extending exhaust slotswith one row located in each half of said stator outward radially fromthe outer row of stator buckets therein and each provided as a baffledaccess extending between the adjacent outer row of rotor buckets and anadjacent exhaust cavity in the respective stator half; a row ofsymmetrically spaced paired fuel mixture diffuser nozzles and ignitionplugs, which divide the turbine into expansion groups, with each pairspaced a predetermined distance apart from one another and extendingaxially through one half only of such stator and terminating in a rowinternal to such stator half adjacent to the adjacent row of ends ofsaid combustion chambers and respectively provided for supplying adiffused compressed elastic fuel mixture to within, and for initiallyigniting such mixture within each of such combustion chambers withinsaid rotor; a plurality of rows of axially extending radial cooling finswith one row extending integral externally with each half of said statormeans for connecting an exhaust manifold to said stator halves and theexhaust cavity in each, and, also to a self actuating, excess airinduction, exhaust diffuser muffler; and, an externally located manuallyoperative means for controlling the number of fuel mixture diffusernozzles and ignition plugs that are placed into and/or out of serviceand simultaneously regulating the proportion of atomized solid fuel thatwill be injected into the fuel mixture being supplied according to thenumber of fuel mixture diffuser nozzles being placed into and/ or out ofservice.

10. The internal combustion turbine of claim 9 characterized by, whereinthe rotor and stator expansion chamber buckets of such turbine are bothof axially extending curved conventional inserted type, with the rotorbuckets thereof curved in the direction of rotor rotation and eachprovided to be secured in axially extending annular shaped serratedgrooves located in both sides of such rotor, and with the stator bucketssimilar but curved in oppositely to rotor rotation and each beingprovided to be secured in similar serrated grooves located in theadjacent sides of said stator halves, and wherein the inner row of suchstator buckets in each stator half is not continuous but is divided intosaid expansion groups, wherein each such group connects the adjacentcombustion chamber ends with the adjacent first row of rotor buckets.

11. The internal combustion turbine of claim 9 characterized by, whereinthe twin tapering nozzles are located at the opposite ends of eachV-shaped combustion chamber and thereby each forms a separate reactionexpansion nozzle and which results in an opposed twin jet type ofreaction diffusion thrust from the expanding products of combustionwithin each combustion chamber during the normal rotative operation ofthe turbine rotor.

12. The internal combustion turbine of claim 9 exemplified by, whereinsaid row of symmetrically spaced paired fuel mixture diffuser nozzlesand ignition plugs, extending through one half only of such stator,divide the turbine stator into a series of circumferentially extendingopposed pairs of pressure velocity compounding expansion groups whichresults in a multitude of relatively small effective explosion impulseswhich per revolution of the rotor is equal to the number of combustionchambers multiplied by twice the number of single expansion groups, andcould be 48 (2 6) and/or 576 of relatively light impulses per eachrevolution of the turbine rotor, so thus the number of power producingimpulses per such revolution of said rotor is doubled by providing suchcombustion chambers to be double ended, likewise the heat distributionwithin the turbine 14 is considerably improved thereby, and the axialthrust on the turbine rotor is balanced due to an.axially opposed systemof group expansion.

13. An internal combustion turbine, operative as the driving means ofand in conjunction with a reversible unit motive power assembly, and,comprising: a relatively narrow, one direction rotative, radiallyextending turbine rotor provided on each side thereof with a series ofannular rows, of increasing in capacities radially outward, of rotorbuckets each curved in the direction of rotor rotation; a row of seriesof through diagonally axially extending V-shaped combustion chamberswith the ends thereof located directly oppositely to one another axiallyand forming an annular row on each side of such rotor and each end ofeach combustion chamber extending diagonally convergingly into theadjacent side of such rotor, in direction of rotation of latter, andterminating together at the point of the V therein such rotor, andwherein each opposite end of each combustion chamber is capable of a jettype reaction diffusion thrust from expanding products of combustionduring the normal rotative operation of such turbine rotor; a pluralityof annular rows of through diagonally axially extending air circulatingholes within said rotor inward radially from said'row of combustionchambers; an axially halved type of annular shaped turbine statorprovided with its periphery closed and its inner radius concentricallysupported and secured, in relation to rotor rotation axis, upon and toan elastic fluid compressor member of and for such turbine, and providedon the adjacent sides of such stator with a series of annular rows, ofsimilarly increasing in capacities, of stator buckets each curved inopposite to the direction of rotor rotation and cooperative with theadjacent rows of rotor buckets; a plurality of rows of axially extendingradial exhaust slots with one row radially outward from each outer rowof stator buckets within such halves of such stator and each row ofslots provided for forming a baffied access extending between theadjacent outer row of rotor buckets and an adjacent exhaust cavity inthe respective stator half; a row of paired diverging fuel mixturediffuser nozzles and ignition plugs with each pair spaced apredetermined distance apart from one another symmetrically about therotor axis and respectively extending diagonally through, in thedirection of rotor rotation, and axially through one half only of suchstator and terminating in an annular row internal to such stator halfadjacent to the inner row of stator buckets therein, and respectivelyprovided for supplying a diffused compressed elastic fuel mixture towithin the adjacent ends of said combustion chambers within said rotor,and for initially igniting such mixture within each such combustionchamber, which mixture is otherwise ignited by direct flame contactmeans; and wherein the turbine is divided into a series of axiallyoppositely located, quandrant shaped twin expansion groups, on eitherside of such rotor, wherein each twin group is provided, in thedirection of rotor rotation, with one fuel diffuser nozzle and oneignition plug, and wherein such an arrangement provides twin groupexpansion within the turbine; a plurality of rows of axially extendingradial cooling fins with one row extending integral externally with eachstator half; an elongated one direction rotatable driving shaft securedto the turbine rotor and extending in common throughout said reversibleunit motive power assembly as the rotatable driving means thereof; meansfor connecting an exhaust manifold, located radially outward to suchstator halves, with each of such exhaust cavities, and to a selfactivating, excess air induction and circulating exhaust diffusermuffler; means for rotatively starting such turbine rotor withcompressed elastic fuel mixture supplied via said fuel diffuser nozzlesto said combustion chambers; and, a jointly operative turbine controland fuel mixture distributing valve unit, for controlling the number offuel v erative check-valve; and; Wherebydujnn m xture d ser no z s andion plu that-haze Pla d into and/or out of service progressively, and irs rnul-v taneously regulating an amount of atomized so d Quid fuel thatwill be pressure atomized and injected intosuch fuel mixturedistributing unit proportionally to the number of fuel mixture diffusernozzles and ignition plugs that are placed into and/or out of servicethereby such glistributing unit; v a

i 14. The internal combustion turbinetof claim 13 characterized by, saidmeans for starting such "turbine rotor with compressed elastic fuelmixture ,supp liedto said combustion chambers, to consist ,Qf: apressure-resera vv oir containing compressed elasticfluid r eiv dQfrgmsaid compressor via said fuel mixture clistri tingt unit through atubing ss qn e ion. whiahl 'ti d r m latter to said reservoir via anon-return ball che e; means connecting latter, below the ball, W'h satservoir via an electrical solenoid coil op ,erz;itive checlevalveg amanually operative electrical push buttonv fo u electricity to thesolenoid coil of such a a g he re ati of said push-button, compressed,elastic is'supplied from such reservoir, via said jointly operativemeans, and via any number ofsaid difluser nozxles s e to each of saidcombustion chambers in sequence as said turbine rotor is rotativelystarted. i

i 15. The internal combustion turbine o f ciairn '13 char,- acterizedby, said means for connecting an exhaust m n fold with each of suchexhaust cavities, inthe stator halves, and to a self activating, excessair induetioln, exhaust difiuser nufller, to consist of: an elongated 0red manifold provided with one end closed and adapted tocvfinfikatexhaus P p ex endi -mm shaped air induction space internal andexternal 0- F16 he hqltq :to'eashr-s grwh l audi snmmt qk f it the: rpecti e xha cav i s o latte a 9 s! 1 .z ato e an qon cn r calr -i'a n derm m d sl n Jilt a yli dric mutflerg tit o p' site-,-n a ann lar shareda n i n pip mr al y an -9 .1mm e muffler end of said exhaust pipe,vvithin such mu ler 4 extending a predetermined distance within latterbeyond the adjacent end of such exhaust pipe andforrningfan annularshaped air induction s a e external tolatter a similar an u haped 2 d ii d c qn'p c comptricaliy-surrou lding the last mentionedlannularfshaped pipe, and extending beyond. latter a predetermined dis?tangewithin'such-mufiler and provided with an an lar $1 h'2ng p pe; at dwn dl m t n a ie a Opposite end of such muifierto saidexhaust pipe;iand, .vvliereby' when exhaustproducts of combustion -are=passing saidau Pip t'o h u f e ex ess. a r' into] latte-r byt self activatingIinduetionJneansQ s ch annul r shaped .airi d bt q m n r a fr b n 3 3 vr bn m' ain e hau t n ibvas 'n sm'bg p 'e n imlas'wqll as ifi i t nd s lnci s h x ai t produc of ik busfim a r A V,

li file of pate t J UNITED STATESPATENTS 2 1 7 fl .-j--.--- 'F 2,1954216 94 Butler l m -M19154

